Guidance and control systems demonstrator for a guided missile

ABSTRACT

1. A functional systems demonstrator for a guided missile of the type having stabilizer wings, control wings and an electronic system for the reception of radiated guidance intelligence and the production and conversion of error signals to control signals comprising, in combination: a support structure including a panel; first means carried on said panel visually demonstrating the derivation of guidance signals by said guided missile; second means carried on said panel and connected with said first means visually demonstrating the production of error signals commensurate with deviations of said missile from a predetermined orientation in a frame of reference; third means carried on said panel visually demonstrating the conversion of said error signals into control signals; and fourth means carried on said panel visually demonstrating the correction of the orientation of the guided missile in response to said control signals.

United States Patent [191 Limouze 1 1 GUIDANCE AND CONTROL SYSTEMS DEMONSTRATOR FOR A GUIDED MISSILE [75] Inventor: Charles A. Limouze, Dearborn,

Mich.

[73] Assignee: The United States of America as represented by the Secretary of the Navy, Washington, DC.

[22] Filed: Dec. 14, 1956 [21] Appl. No.: 628,470

[52] U.S. CI. 35/l0.4; 35/12 R [51] Int. Cl. G09b 9/00 [58] Field of Search i. 35/l0.4, l2, 12 R, 12 B, 35/12 S [56] References Cited UNITED STATES PATENTS 2,602,243 7/1952 Link 35/l().4 2,780,011 2/1957 Pierce et a1 35/10.4

Primary Examiner-Malcolm F. I-Iubler Attorney, Agent, or Firm-R. S. Sciascia; L. S. Epstein; J. A. OConnell May 20, 1975 EXEMPLARY CLAIM l. A functional systems demonstrator for a guided missile of the type having stabilizer wings, control wings and an electronic system for the reception of radiated guidance intelligence and the production and conversion of error signals to control signals comprising, in combination: a support structure including a panel; first means carried on said panel visually demonstrating the derivation of guidance signals by said guided missile; second means carried on said panel and connected with said first means visually demonstrating the production of error signals commensurate with deviations of said missile from a predetermined orientation in a frame of reference; third means carried on said panel visually demonstrating the conversion of said error signals into control signals; and fourth means carried on said panel visually demonstrating the correction of the orientation of the guided missile in response to said control signals.

12 Claims, 6 Drawing Figures GUIDANCE r z Q 4 BEAM VERNIER o MIS 5.11.2 POSI TIOIIHG FLY summer ac. PULS ONLY EQUI YHLENTS 2500 CPS ass/Luann I In a is 180 our 0F PHASE MODULATORS ID in m m mmm s, .3, 883 961 SHEET 2 OF 5 I I 0 II 6 a Q a a 10 M QY F1255 201.1. FREE P/TcH-mw GYRO GYRO 1r YAW U g- H Ml U v .45 J- FREE 6720 72, 2 500 CPS a n/g1 l 5 202 MOD LA 5 a PITCH a 4r COMPONENT RESOLVER 54 '8 i I Q A PITCH n W d3 RQTE qmos I. SERVO AMPLIFIER 7 68 7'0 7] z. wnvq FEEDBACK POTS a. ACOELEROMETERS M finals mam/c9 M A WA ALL GYROS mu. Bv yaw PITCH RIGHT-PITCH WING AgTUAToR T wk? J V ACOUMULATOR OPERATED SOLENOID VALVE CONTROL VALVE 91 I INVENTOR. 14

CHARLES A. )JMOUZE v a BY 3 OCWQ J j NEXS PNENHZQ HAYZOlQTE 1N VEN TOR.

CHARLES A. LIMOUZE W/FW/ mw my a e a R T 7'02 NUS GUIDANCE AND CONTROL SYSTEMS DEMONSTRATOR FOR A GUIDED MISSILE This invention relates to a device for demonstrating the operation of functional systems of a guided missile.

The invention will be described in relation to a guidance and control systems demonstrator for a guided missile of the Sparrow I type, but it is to be understood that the invention is not necessarily limited to a demonstrator for this particular missile.

Because the subject of guided missiles is relatively new, an instructor is frequently faced with the problem of supplying the students with a basic concept of missiles at the same time that he is teaching more detailed or technical aspects. Unlike the instructor of more conventional aircraft, he cannot assume that the students will have even a general knowledge of the subject. He cannot, for example, speak of the glide of a missile and expect the students to picture a powerless, supersonic flight like that of the Sparrow. Nor can he use so common a term as wing without risking a misinterpretation on the part of the students.

To assist the instructor in his task of acquainting the students with the principles of operation of the guidance and control systems of a Sparrow-type guided missile, the present demonstrator has been developed.

The invention comprises a demonstration panel containing fabricated simulations of mechanisms which are component parts of various functional systems of the guided missile. The simulations are operable to visibly illustrate the functioning of the simulated mechanisms in the missile. A block schematic diagram on the panel illustrates the guidance and control systems, the fabricated simulations being properly located with respect to the diagram.

The effect on the guidance pulses and error signals of change in the position of the missile relative to the nutational axis of the radar guidance beam is indicated by simulated oscilloscopes and meters.

An object of this invention is to provide a training aid which instructors may employ advantageously in demonstrating to students the operation of functional systems of a guided missile.

Another object is to provide apparatus which simulates components of the functional systems of a guided missile and visibly demonstrates their operation.

A further object is to provide apparatus which simulates the guidance and control system components of a Sparrow-type guided missile and visibly demonstrates their operation and interrelationship.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. la-c is a perspective drawing of a preferred embodiment of the invention, showing the demonstrator panel in detail,

FIG. 2 is a diagrammatic representation of the rear of the demonstrator panel,

F lG. 3 is a diagrammatic representation of the oscilloscope wire-and-pulley system, and

FIG. 4 is a schematic circuit diagram showing the electrical wiring of the demonstrator.

Similar reference characters in the various figures refer to similar elements.

GENERAL The missile guidance and control systems demonstrator (see FIG. 1) comprises a rectangular frame bear- 5 ing a panel consisting of an upper part called a demonstrator panel 12 and subpanel 14 containing the main power switch 16, a motor switch 18, a spare parts container and a chart container 22. in the chart container 22 are eight color transparencies illustrating the sequence of events which may occur in the actual operational situation in which a Sparrow missile is employed from the time a target is found by the launching aircraft to the destruction of the target or missile. They may be used in conjunction with the demonstrator 10, or independently.

The events illustrated by the eight color transparencies are as follows:

a. Searching (and stand-by position). This is the point at which a potential target becomes known to the pilot. The equipment activated in the missile is listed.

b. Acquisition. The target is captured by the radar beam. Activated equipment is the same as at searching.

c. Fire. The firing button is pressed. The events that take place in the missile prior to launching are listed.

d. Launch. The umbilical cord is separated. Launching events are listed.

e. Thrust (autopilot phase). Functional components of the automatic pilot are indicated in color. Function switch 24 is at thrust.

f. Guidance 2.2 seconds after firing. Functional components of the guidance system are indicated in color. The function switch 24 is on guidance.

g. Proximity destruction. The missile reaches the target and explodes.

h. Self-destruction. The self-destructor is activated automatically when the missile leaves the beam.

A block diagram on the demonstrator panel 12 shows the inter-relation of the components of the guidance and control systems. A missile positioning mechanism, a pitch-roll-yaw mechanism and a control-wings mechanism are worked into the block diagram. The block diagram and associated mechanisms serve to illustrate functionally; (l) the receipt of intelligence by the missile from the target-tracking radar beam, (2) the opera tion of the thrust automatic pilot, and (3) theconversion in the missile of signals from the beam rider system and automatic pilot to control signals for actuating the control wings.

DEMONSTRATOR PANEL FRONT The Missile-Positioning Mechanism The missile positioning mechanism on the upper left side of the demor1strator panel 12 is used in conjunction with eight simulated rectangular oscilloscopes (guidance pulse oscilloscopes 26 and dc. equivalent oscilloscopes 28) and two dials 30 and 32 (for the leftright and up-down 2500 c.p.s. error modulated signals, respectively). Each dial has a Phase A (A) and a Phase B bB) indicator lamp 34 and 36 respectively associated with it. Magnitude of the guidance pulses and dc. equivalents is shown by movement of the simulated oscilloscopes 26 and 28, and magnitude of the modulated signal is shown by pointer movement. The four indicator lights show the phase of the modulated signal.

The phases of the signals correspond to positions of the missile with respect to the coordinate axes of a frame of reference (spatial coordinate system) having an orientation relative to the nutating radar guidance beam which is determined at the moment the missile is launched.

The missile positioning mechanism consists of an animated representation or simulation of a Sparrow missile 38, viewed from the rear, in relation to a simulated beam area 40. A colored plastic disk simulating the actual radar beam 42 sweeps continuously at about 40 revolutions per minute. Tracking and guidance pulses, 44 and 46 respectively, are indicated graphically on the circumference of the beam area 40. The missile can be moved to any position in the beam area 40 by turning two control knobs, the left-right control knob 48 or the up-down control knob 50, which are located along the left side of the panel directly beneath the rotating beam area 40. The beam 42 can be stopped at any point in its sweep by turning off the motor switch 18 and then manipulating the beam vemier knob 52, which manually rotates the beam area 40.

The eight rectangular simulated oscilloscopes are connected mechanically to the missile positioning mechanism so that the relative amplitude and spacing of guidance pulses are visualized for any missile position. Four rectangular oscilloscopes 26 show voltages proportional to the missiles deviation from the center of the beam as up-down-left-right guidance pulses, and the other four 28 show the dc. equivalents of those guidance pulses. Up-down and left-right 2500 c.p.s. error modulated signals are illustrated by an up-down and a left-right dial, 30 and 32 respectively. Variations in the amplitude of the modulated signal are shown by pointers on the dials, and phase changes are shown by two indicator lights (11 A 34 and 4) B 36) for each dial. The phase changes correspond to missile position changes from up to down, or from left to right, or vice versa.

The Pitch-Roll-Yaw Mechanism A simulation of the stabilizer wing section 54 of the missile, mounted near the center of the panel, is connected by a mechanical electrical system to meters which show the operation of the three rate gyros, two accelerometers and two free gyros. The three rate gyros, roll rate gyro 66, yaw rate gyro 68 and pitch rate gyro 70, are fabricated simulations or models of the rate gyros in the missile, and may be made of any suitable material or combination of materials, such as plastic, metal, wood, etc. Each has a separate meter associated with it, i.e., the roll-rate-gyro meter 56, the yawrate-gyro meter 58 and the pitch-rate-gyro meter 70 respectively.

The stabilizer-wing section simulation 54 can be moved to illustrate missile pitch, roll, or yaw. The motion of the missile about the pitch axis shows acceleration on the normal accelerometer meter 62, which is located in the upper right hand area of the panel 12. The motion of the missile about the yaw axis shows acceleration on the lateral accelerometer meter 64, which is located just above the normal accelerometer meter 62.

The Block Diagram The block diagram on the demonstrator panel 12 illustrates how signals from the beam rider system, the

rate gyros, and the automatic pilot are converted to control signals and transmitted to the control wings of the missile. The units illustrated in the block diagram are the guidance preamplifier 81, the summing amplifier 87, the servo amplifier unit 89 and the hydraulic accumulator 91.

Supplementary to the block diagram are a manually operated simulated function switch 24 and a variable pressure unit 93. The function switch 24 demonstrates what happens electrically when the missile mode of operation is changed from autopilot to beam rider at the end of the thrust period.

The Control-Wings Mechanism At the lower right side of the demonstrator panel 12, a simulation of the control-wings section of the missile shows how the four control surfaces are actuated by three hydraulic solenoid servos. The two yaw control wings are connected mechanically to the yaw wing actuator piston 97 in the lower right-hand corner of the panel 12, and their joint action can be demonstrated by moving the actuator piston 97. In a similar manner, the right and left pitch wings are connected respectively and independently to the right pitch wing actuator piston 99 and the left pitch wing actuator piston 101. The hydraulic solenoid plungers, e.g., the plunger 103 for the solenoid associated with the yaw wing actuator piston 97, can be moved manually to show how the flow of fluid to the actuator pistons is controlled.

DEMONSTRATOR PANEL REAR The Missile-Positioning Mechanism The details of the missile-positioning mechanism are illustrated in FIG. 2. The simulated radar beam area 40, a large plastic disc with a circular plastic insert 42 representing a radar beam, is rotated by means of a motor.

The animated missile simulation 38 is mounted behind the beam area disc 40 on a carriage 78 and is free to move on rollers or sliders horizontally along the carriage 78. At the same time, the entire carriage 78 may be moved up or down along a pair of vertical guides 80 and 82. The horizontal moving force is supplied through the L-R control knob 48 and transmitted to the animated missile simulation 38 by means of a system of pulleys 84 and a wire 86. The vertical moving force is supplied through the DN-UP control knob 50 and transmitted to the carriage 78 by a second system of pulleys 88 and another wire 90.

The eight simulated oscilloscopes comprise a series of eight graphic representations of the guidance pulses and their d.c. equivalents painted or otherwise impressed upon material such as cloth or paper wound upon eight drums 92, 94, 96, 98, 100, 102, 104, and 106. The drums are mounted in pairs on four drum shafts 108, 110, 112, 114. The drum shafts are rotated in pairs, a down-up pair 108 and 112 and a left-right pair 110 and 114. Each shaft in a pair rotates in the opposite direction from its mate so that, for example, if the Fly Left signal amplitude is increased, the Fly Right signal amplitude is correspondingly decreased. The drum shafts 108, 1 10, 112 and 114 are coupled to the movements of the animated missile simulation 38 by means of wire-and-pulley systems as shown in FIG. 3. The DN-UP shafts 108 and 112 are turned by DN-UP shaft drive pulleys 116 and 120 respectively, which are driven by the oscilloscope system down-up drive wire 124, which, in turn, derives its actuating force from the oscilloscope system down-up drive pulley 126. Pulley 126 is driven by the missile-positioning down-up wire-and-pulley system. The L-R shafts 110 and 114 are turned by left-right shaft drive pulleys 118 and 122 respectively, which are driven by the oscilloscope system left-right drive wire 128, which, in turn, derives its actuating force from the oscilloscope system left-right drive pulley 130. Pulley 130 is driven by the missile-positioning left-right wire and pulley system.

Power is applied to the down-up dJA and d B indicator lamps 34 and 36 through a rotary switch, the down-up phase-lamp switch 132. This switch 132 has two arcuate contacts, each covering about 175 in length and spaced from the other. The contacts and the intermediate spaces form a circle along which the contact arm is driven by mechanically coupling it to the oscilloscope down-up drum shaft 112, or by any other means coupling it to the missile-positioning or oscilloscope downup drive systems. Care must be taken in the initial adjustment, of course, to locate the contact arm in the space between the contacts when the missile simulation 38 is in the center of the beam area 40 and the amplitudes of the guidance signals are equal.

Similarly, power is applied to the left-right phase indicator lamps through the left-right phase-lamp switch 134 which is mechanically coupled to the oscilloscope left-right drum shaft 114.

The down-up and left-right phase dial pointers 31 and 33, which indicate the amplitudes of the two error modulated 2500 c.p.s. signals, are driven by means of a down-up and a left-right Geneva movement 136 and 138 respectively. These Geneva movements are actuated by the oscilloscope drum shafts.

One or more small light sources (not shown) such as incandescent lights, are secured behind the animated missile simulation 38 so that all travel together and the shape of the simulation 38 is visibly projected upon the simulated radar beam area 48.

The Pitch-Roll-Yaw Mechanism The stabilizer wing simulation 54 is mounted in a gimbal system 140 so that the simulation 54 may be rotated about the pitch, roll or yaw axis shafts. A flexible coupling shaft and a potentiometer are affixed to each axis shaft. For example, a roll-indicating flexible coupling shaft 142 and roll potentiometer 144 are coupled to the roll axis shaft. The roll-indicating flexible coupling shaft 142 is connected at the other end to the free-roll-gyro component resolver 146.

Similarly, the pitch-indicating flexible coupling shaft 146 couples pitch axis movements to the dial of the pitch potentiometer simulation 72, and the yawindicating flexible coupling shaft 150 couples yaw axis movements to the dial of the yaw-potentiometer simulation 74. Pitch potentiometer 148 and yaw potentiometer 150 are coupled to the pitch and yaw axis shafts respectively.

The fabricated roll, yaw and pitch rate gyros 66, 68 and 70 are associated with lever arms 67, 69 and 71, respectively, which project from the front of the panel 12. Each lever arm is mechanically coupled to a potentiometer, so that the potentiometer contact arm is rotated by movement of the lever arm. Thus, the roll gyro lever arm 67 is coupled to the roll gyro potentiometer 154, the yaw gyro lever arm 69 to the yaw gyro potentiometer 156 and the pitch gyro lever arm 71 to the pitch gyro potentiometer 158.

FIG. 4 shows how the meters and potentiometers are electrically wired.

As the stabilizer-wing simulation 54 is moved, the stabilizer-wing simulation potentiometer on the affected axis is rotated. This varies the current through the corresponding meter which deflects from its zero position to indicate a rate change either toward A or B depending on the direction of missile movement. When missile motion ceases, the meter returns to zero regardless of the actual position of the stabilizer-wing simulation 54.

The normal and lateral accelerometer meters 62 and 64 are also galvanometers which are connected in par allel with the pitch and yaw rate-gyro meters 60 and 58, respectively. These meters 62 and 64 also indicate rate changes along their associated axes and return to zero when missile motion ceases.

Movement of the rate-gyro lever arm causes rotation of the contact arm of its associated rate-gyros potentiometer and a current variation in its associated rategyro galvanometer. This displaces the meter needle toward the proper phase, the needle remaining displaced unit] the lever arm is returned to its center, or zero, position.

Thus, for example, if the stabilizer-wing simulation 54 is moved along the yaw axis, yaw potentiometer 152 is moved from its central, or zero potential position (i.e. zero potential because of its balanced position in a resistive bridge circuit). This causes a charging current to flow through the yaw rate-gyro meter 58 and through the lateral accelerometer meter 64, both of which indicate momentary deflections and then return to zero position.

If the lever arm 69 of the yaw rate gyro 68 is moved off its zero position, a momentary deflection of the lateral accelerometer meter 64 and a constant deflection of the yaw rate-gyro meter 58 occur. The constant deflection is proportional to the extent of movement of the lever arm 69 from its zero position and the meter 58 does not return to zero until the lever arm 69 is returned to its central position.

The Control-Wings Mechanism Each wing actuator piston is mechanically linked to a pulley-and-wire drive system mounted on the rear of the demonstrator panel 12. The wire is fastened to and moves the corresponding control wing on the controlwing simulator in the proper direction. Thus, the yaw-wing-actuator piston 97 drives the yaw-controlwing drive pulley and wire 107 to jointly move the yaw control wings on the control-wing simulator 95. Similarly, there is a pulley 109 and wire 111 for controlling the right pitch wing and a pulley 113 and wire 115 for controlling the left pitch wing. The pitch wings are independently controlled.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

I claim:

1. A functional systems demonstrator for a guided missile of the type having stabilizer wings, control wings and an electronic system for the reception of radiated guidance intelligence and the production and conversion of error signals to control signals comprising, in combination: a support structure including a panel; first means carried on said panel visually demonstrating the derivation of guidance signals by said guided missile; second means carried on said panel and connected with said first means visually demonstrating the production of error signals commensurate with deviations of said missile from a predetermined orientation in a frame of reference; third means carried on said panel visually demonstrating the conversion of said error signals into control signals, and fourth means carried on said panel visually demonstrating the correction of the orientation of the guided missile in response to said control signals.

2. A functional systems demonstrator for a guided missile of the type having stabilizer wings, control wings comprising right and left pitch and yaw wings and an electronic system for the reception of guidance pulses, and the production and conversion of error signals to control signals comprising, in combination: a support structure including a panel; means carried on said panel visually demonstrating the derivation of guidance signals by said guided missile including means simulating a nutating radar beams, movable means situated within the area covered by said mutating radar beam simulating the guided missile, means responsive to the motion of said movable means indicating the amplitudes of said guidance pulses and their derived equivalent signals, said pulses varying in accordance with the orientation of said missile with respect to a predetermined frame of reference relating to the radar beam nutation axis, and a first section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to derive the guidance signals; means carried on said panel visually demonstrating the production of error signals commensurate with deviations of said missile from a predetermined orientation in a frame or reference, said last-named means including means simulating a section of the guided missile bearing the stabilizer wings and manipulable to produce signals corresponding to the yaw, pitch and roll rate error signals produced in the guided missile, means operable in response to yaw and pitch movements of said stabilizerwing simulating means simulating the yaw and pitch ertor-signal generators of the missile, means simulating the rate gyros of the guided missile and having associated means generating signals corresponding to the yaw, pitch and roll error signals produced in the missile, means indicating the signals produced by said stabilizer-wing simulating means and said rate-gyro simulating means, means simulating a pressure-responsive unit generating signals correcting said yaw, pitch and roll error signals in accordance with atmospheric and altitudinal pressure factors, a second section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to produce the error signals, including a portion showing conversion of said guidance pulses to guidance-pulse error signals, and means indicating characteristics of said guidance-pulse error signals; means carried on said panel visually demonstrating the conversion of said error signals into control signals including a third section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to convert the error signals into control signals; and means carried on said panel visually demonstrating the correction of the orientation of said guided missile in response to said con trol signals including manipulable means simulating mechanisms for independently positioning the right pitch wing, the left pitch wing and the yaw wings conjointly of the missile, manipulable means simulating the mechanisms controlling the application of activating energy to said wing-positioning mechanisms in response to said control signals, means simulating a section of the missile bearing the control wings, the position of said wings being movable in response to manipulations of said wing-positioning mechanism simulations, and a fourth section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to correct the orientation of the control wings in response to the control signals.

3. A device as set forth in claim 2, wherein: said means simulating a nutating radar beam includes a first circular disc representing the entire cross-sectional area covered by the nutating beam, a second smaller circular disc representing the cross-sectional area of the radar beam itself, said second disc affixed to said first disc so that the circumferences of the'two discs are tangent, both discs being translucent and mounted to the rear of said panel but visible from the front, and motor means mounted on the rear of said panel operating to rotate said discs; said means simulating the guided missile includes a third disc having the crosssectional shape of the missile, carriage means comprising a horizontal track movable vertically across the area covered by said first disc and a conveyer movable horizontally on said track across the area covered by said first disc, said conveyer bearing with it said missileshaped disc and light means projecting the image of said missile-shaped disc upon said first and second discs, a wire-and-pulley system operatively associated with said carriage means, and control means coupled and applying power to said wire-and-pulley system, whereby said carriage means and said missile-shaped disc are caused to move correspondingly; and said means indicating the amplitudes of said guidance pulses and said equivalent signals includes a plurality of graphic representations of guidance pulses and their derived equivalent signals located behind cut-outs in said support panel, the lower edges of said cut-outs serving as a zero reference line for said pulses and signals, a plurality of shafts bearing coaxial drums around which said graphic representations are securely wrapped for viewing through said cut-outs, and a wireand-pulley system operatively associated with said wire-and-pulley system moving said missile-shaped disc for moving said shafts in accordance with the movements of said missile-shaped disc.

4. A device as set forth in claim 2, wherein: said means simulating the stabilizer wing section of the missile comprises a fabricated imitation of the transverse section of said missile containing the stabilizer wings, a gimbal system mounting said imitation for yaw, pitch and roll movements, means operatively associated with said gimbal system producing signals in response to the yaw, pitch and roll movements of said imitation, and means operatively associated with said gimbal system producing torsions in response to the yaw, pitch and roll movements of said imitation; said means simulating the yaw and pitch error-signal generators of the missile comprises representations of otentiometers having movable simulations of contact arms, said arms being operatively connected to said torsion-producing means; said means simulating the rate gyros of the guided missile comprises fabricated models of the rate gyros of the missile, each with its spinning axis in a different position so that each resists a different one of the three possible movements of the missile, yaw, pitch or roll, and said means generating signals corresponding to the yaw, pitch and roll error signals produced in the missile comprises Potentiometers, each having its contact arm connected to a movable lever projecting from the panel; said means indicating the signals produced by said stabilizer-wing simulating means comprises a plurality of electrical meters deflectable in either direction from a zero position at mid-scale; said means simulating a pressure-responsive unit comprises a flat, bullet-shaped member having a central aperture connected with its outer edge and a movable piston retained in said aperture; and said means indicating characteristics of said guidance-pulse error signals comprises a pair of dial representations, each associated with a pair of indicator lamps, said dial representations showing guidance-pulse error signal amplitude by means of pointers effectively operated by said wireand-pulley system moving said missile-shaped disc, one dial associated with the updown positioning system and one dial with the left-right positioning system, and each indicator lamp in a pair indicating a different phase of the guidance-pulse error signals, said signals being connected to the correct indicator lamp by switch means effectively operated by said wire-andpulley system moving said missile-shaped disc.

5. A device as set forth in claim 2, wherein: said means simulating wing-positioning mechanisms comprises a trio of fabricated flat members mounted on the front of said panel, each member rectangularly shaped like the cross-section of a piston chamber and containing a manually movable piston within its central aperture; said means simulating activating-energy control mechanisms comprises a trio of simulations of solenoid-operated hydraulic pressure valves consisting of fabricated flat members mounted on the front of said panel, each member rectangularly shaped like the cross-section of a piston chamber and containing a manually movable piston within its central aperture, and each member adjacent to a different one of the wing-psitioning-mechanism simulations and operatively associated with it so as to illustrate by movement of said piston the manner in which application of hydraulic pressure to said mechanism is controlled; and said means simulating the control wing section of the missile comprises a fabricated imitation of the transverse section of said missile containing the control wings and wire-and-pulley systems connecting each of said pistons in said wing-positioning-mechanism simulations to its respective wing so that manual movement of a piston correspondingly positions its associated wing.

6. A functional systems demonstrator for a radarguided missile of the type having stabilizer wings, control wings comprising left and right yaw and pitch wings and an electronics system for the reception of guidance intelligence and the production and conversion of error signals to control signals comprising, in combination: a supporting structure including a demonstration panel; a missile-positioning mechanism supported by said panel demonstrating the manner in which the characteristics of the received guidance intelligence and its equivalent derived signals vary in accordance with the position of the missile relative to the radar beam; a pitch-roll-yaw mechanism supported by said panel demonstrating the production of error signals in response to deviations of the missile from a predetermined reference altitude relative to the radar beam axis; a control-wings mechanism supported by said panel demonstrating the manner in which the control signals effect changes in the attitudes of the control wings relative to the body of the missile; and a block diagram of the guidance and control system of the missile, depicted on said panel and illustrating the components and stages utilized to accomplish the reception of guidance intelligence and the production and conversion of error signals to control signals, the interrelationship of said mechanisms and their output signals with the components and stages in said block diagram being shown by means of connecting lines.

7. A device as set forth in claim 6, wherein said missile-positioning mechanism includes: means simulating a nutating radar beam; means movable within the area covered by said nutating radar beam simulating the guided missile; and means responsive to the motion of said movable means indicating the changes which occur in the characteristics of the received guidance intelligence and the equivalent derived signals when the means simulating the guided missile is moved within the radar beam area.

8. A device as set forth in claim 6, wherein said pitchroll-yaw mechanism includes: means simulating the stabilizer-wing section of the guided missile, said means being manipulable in the yaw, pitch and roll planes to produce signals corresponding to the yaw, pitch and roll rate error signals produced in the guided missile; means, operable in response to movements of said stabilizer-wing simulating means in the yaw and pitch planes, simulating the yaw and pitch error-signal generators of the guided missile; means simulating the rate gyros of the guided missile and having associated means generating signals corresponding to the yaw, pitch and roll error signals produced in the guided missile; and means indicating the signals produced by said stabilizer-wing simulating means and said rate-gyro simulating means.

9. A device as set forth in claim 6, wherein said control-wings mechanism includes: means simulating the control-wings section of the guided missile, the control wings thereon being movable; manipulable means simulating the control-wings positioning mechanism in the guided missile, manipulation of said last-named means operating to move the wings on said control wings simulating means; and manipulable means simulating the mechanisms in the missile which control the application of activating energy to said wing-positioning mechanism in response to said control signals.

10. A device as set forth in claim 6, wherein said missile-positioning mehanism includes: a first circular disc representing the entire transverse cross-sectional area covered by a nutating radar beam; a second smaller circular disc representing the transverse cross-sectional area of the radar beam itself, said second disc affixed to said-first disc so that the circumference of the former is circumscribed by and tangent to the circumference of the latter, both discs being translucent and mounted to the rear of said panel but visible from the front; motor means mounted on the rear of said panel operating to rotate said discs; a third disc having the crosssectional shape of the guided missile; carriage means comprising a horizontal track movable vertically across the area covered by said first disc and a conveyer movable horizontally said track across the area covered by said first disc, said conveyer bearing with it said missileshaped disc and light means projecting the image of said missile-shaped disc upon said first and second discs; a wire-and-pulley system operatively associated with said carriage means; control means coupled and applying power to said wire-and-pulley system, whereby said carriage means and said missile-shaped disc are caused to move correspondingly; a plurality of graphic representations of the guidance pulses constituting the received guidance intelligence and a plurality of graphic representations of their derived equivalent signals, said representations located behind cut-outs in said support panel, the lower edges of said cut-outs serving as a zero reference level for said pulses and signals; a plurality of shafts bearing coaxial drums to which said representations are affixed for viewing through said cut-outs; a wire-and-pulley system, operatively associated with said wire-and-pulley system moving said missile-shaped disc, moving said shafts in accordance with the movements of said missile-shaped disc; and a pair of dial representations, each associated with a pair of indicator lamps, said dial representations showing guidance-pulse error signal amplitude by means of pointer effectively operated by said Wire-andpulley system moving said missile-shaped disc, one dial associated with the up-down positioning system and one dial with the left-right positioning system, and each indicator lamp in a pair indicating a different phase of the guidance-pulse error signals, said signals being connected to the correct indicator lamp by switch means effectively operated by said wire-and-pulley system moving said missile-shaped disc.

11. A device as set forth in claim 6, wherein said pitch-roll-yaw mechanism includes; a fabricated imitation of a transverse section of said missile containing the stabilizer wings; a gimbal system mounting said imitation for yaw, pitch and roll movements; means operatively associated with said gimbal system producing signals in response to the yaw, pitch and roll movements of said imitation; means operatively associated with said gimbal system producing torsions in response to the yaw, pitch and roll movements of said imitation; a

plurality of potentiometer representations having movable simulations of contact arms, said arms being operatively connected to said torsion-producing means; fabricated models of the rate gyros of the missile, each with its spinning axis in a different position so that each resists a different one of the three possible movements of the missile, yaw, pitch or roll; a plurality of levers projecting from said panel, each adjacent to and associated with a respective rate-gyro model, and a plurality of potentiometer means, each having a contact arm connected to be moved by a respective lever for the production of signals corresponding to the yaw, pitch and roll error signals produced in the missile; a plurality of electrical meters indicating the signals produced by said means associated with said gimbal system and said potentiometer means; and a flat, bullet-shaped member having a central aperture connected with its outer edge and a movable piston retained in said aperture representing the missiles pressure-responsive error-signal generator.

12. A device as set forth in claim 6, wherein said control-wings mechanism includes: a plurality of fabricated flat members mounted on the front of said panel, and representing the missile wing-actuating mechanisms, each member rectangularly shaped like the cross section ofa piston chamber and retaining a manually movable piston within its central aperture; a plurality of fabricated flat members mounted on the front of said panel and representing the missiles mechanisms for controlling the application of activating energy to its wing-actuating mechanisms, each member rectangularly shaped like the cross-section of a piston chamber and retaining a manually movable plunger within its central aperture; means indicating how movement of said plungers controls the communication of activating energy to said pistons; means indicating that said plungers are operable in response to said control signals; a fabricated imitation of the transverse section of the missile containing the control wings, the wings on said imitation being movable as in said missile; and wireand-pulley systems connecting each of said pistons in said wing-positioning-mechanism representations to its respective wing so that manual movement of a piston correspondingly positions its associated wing. 

1. A functional systems demonstrator for a guided missile of the type having stabilizer wings, control wings and an electronic system for the reception of radiated guidance intelligence and the production and conversion of error signals to control signals comprising, in combination: a support structure including a panel; first means carried on said panel visually demonstrating the derivation of guidance signals by said guided missile; second means carried on said panel and connected with said first means visually demonstrating the production of error signals commensurate with deviations of said missile from a predetermined orientation in a frame of reference; third means carried on said panel visually demonstrating the conversion of said error signals into control signals, and fourth means carried on said panel visually demonstrating the correction of the orientation of the guided missile in response to said control signals.
 2. A functional systems demonstrator for a guided missile of the type having stabilizer wings, control wings comprising right and left pitch and yaw wings and an electronic system for the reception of guidance pulses, and the production and conversion of error signals to control signals comprising, in combination: a support structure including a panel; means carried on said panel visually demonstrating the derivation of guidance signals by said guided missile including means simulating a nutating radar beams, movable means situated within the area covered by said mutating radar beam simulating the guided missile, means responsive to the motion of said movable means indicating the amplitudes of said guidance pulses and their derived equivalent signals, said pulses varying in accordance with the orientation of said missile with respect to a predetermined frame of reference relating to the radar beam nutation axis, and a first section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to derive the guidance signals; means carried on said panel visually demonstrating the production of error signals commensurate with deviations of said missile from a predetermined orientation in a frame or reference, said last-named means including means simulating a section of the guided missile bearing the stabilizer wings and manipulable to produce signals corresponding to the yaw, pitch and roll rate error signals produced in the guided missile, means operable in response to yaw and pitch movements of said stabilizer-wing simulating means simulating the yaw and pitch error-signal generators of the missile, means simulating the rate gyros of the guided missile and having associated means generating signals corresponding to the yaw, pitch and roll error signals produced in the missile, means indicating the signals produced by said stabilizer-wing simulating means and said rate-gyro simulating means, means simulating a pressure-responsive unit generating signalS correcting said yaw, pitch and roll error signals in accordance with atmospheric and altitudinal pressure factors, a second section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to produce the error signals, including a portion showing conversion of said guidance pulses to guidance-pulse error signals, and means indicating characteristics of said guidance-pulse error signals; means carried on said panel visually demonstrating the conversion of said error signals into control signals including a third section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to convert the error signals into control signals; and means carried on said panel visually demonstrating the correction of the orientation of said guided missile in response to said control signals including manipulable means simulating mechanisms for independently positioning the right pitch wing, the left pitch wing and the yaw wings conjointly of the missile, manipulable means simulating the mechanisms controlling the application of activating energy to said wing-positioning mechanisms in response to said control signals, means simulating a section of the missile bearing the control wings, the position of said wings being movable in response to manipulations of said wing-positioning mechanism simulations, and a fourth section of the missile guidance and control system block diagram showing the interrelationship of components and stages utilized to correct the orientation of the control wings in response to the control signals.
 3. A device as set forth in claim 2, wherein: said means simulating a nutating radar beam includes a first circular disc representing the entire cross-sectional area covered by the nutating beam, a second smaller circular disc representing the cross-sectional area of the radar beam itself, said second disc affixed to said first disc so that the circumferences of the two discs are tangent, both discs being translucent and mounted to the rear of said panel but visible from the front, and motor means mounted on the rear of said panel operating to rotate said discs; said means simulating the guided missile includes a third disc having the cross-sectional shape of the missile, carriage means comprising a horizontal track movable vertically across the area covered by said first disc and a conveyer movable horizontally on said track across the area covered by said first disc, said conveyer bearing with it said missile-shaped disc and light means projecting the image of said missile-shaped disc upon said first and second discs, a wire-and-pulley system operatively associated with said carriage means, and control means coupled and applying power to said wire-and-pulley system, whereby said carriage means and said missile-shaped disc are caused to move correspondingly; and said means indicating the amplitudes of said guidance pulses and said equivalent signals includes a plurality of graphic representations of guidance pulses and their derived equivalent signals located behind cut-outs in said support panel, the lower edges of said cut-outs serving as a zero reference line for said pulses and signals, a plurality of shafts bearing coaxial drums around which said graphic representations are securely wrapped for viewing through said cut-outs, and a wire-and-pulley system operatively associated with said wire-and-pulley system moving said missile-shaped disc for moving said shafts in accordance with the movements of said missile-shaped disc.
 4. A device as set forth in claim 2, wherein: said means simulating the stabilizer wing section of the missile comprises a fabricated imitation of the transverse section of said missile containing the stabilizer wings, a gimbal system mounting said imitation for yaw, pitch and roll movements, means operatively associated with said gimbal system producing signals in response to the yaw, pitch and roll movements of said imitation, and means operatively associated with said gimbal system producing torsions in response to the yaw, pitch and roll movements of said imitation; said means simulating the yaw and pitch error-signal generators of the missile comprises representations of potentiometers having movable simulations of contact arms, said arms being operatively connected to said torsion-producing means; said means simulating the rate gyros of the guided missile comprises fabricated models of the rate gyros of the missile, each with its spinning axis in a different position so that each resists a different one of the three possible movements of the missile, yaw, pitch or roll, and said means generating signals corresponding to the yaw, pitch and roll error signals produced in the missile comprises potentiometers, each having its contact arm connected to a movable lever projecting from the panel; said means indicating the signals produced by said stabilizer-wing simulating means comprises a plurality of electrical meters deflectable in either direction from a zero position at mid-scale; said means simulating a pressure-responsive unit comprises a flat, bullet-shaped member having a central aperture connected with its outer edge and a movable piston retained in said aperture; and said means indicating characteristics of said guidance-pulse error signals comprises a pair of dial representations, each associated with a pair of indicator lamps, said dial representations showing guidance-pulse error signal amplitude by means of pointers effectively operated by said wire-and-pulley system moving said missile-shaped disc, one dial associated with the up-down positioning system and one dial with the left-right positioning system, and each indicator lamp in a pair indicating a different phase of the guidance-pulse error signals, said signals being connected to the correct indicator lamp by switch means effectively operated by said wire-and-pulley system moving said missile-shaped disc.
 5. A device as set forth in claim 2, wherein: said means simulating wing-positioning mechanisms comprises a trio of fabricated flat members mounted on the front of said panel, each member rectangularly shaped like the cross-section of a piston chamber and containing a manually movable piston within its central aperture; said means simulating activating-energy control mechanisms comprises a trio of simulations of solenoid-operated hydraulic pressure valves consisting of fabricated flat members mounted on the front of said panel, each member rectangularly shaped like the cross-section of a piston chamber and containing a manually movable piston within its central aperture, and each member adjacent to a different one of the wing-positioning-mechanism simulations and operatively associated with it so as to illustrate by movement of said piston the manner in which application of hydraulic pressure to said mechanism is controlled; and said means simulating the control wing section of the missile comprises a fabricated imitation of the transverse section of said missile containing the control wings and wire-and-pulley systems connecting each of said pistons in said wing-positioning-mechanism simulations to its respective wing so that manual movement of a piston correspondingly positions its associated wing.
 6. A functional systems demonstrator for a radar-guided missile of the type having stabilizer wings, control wings comprising left and right yaw and pitch wings and an electronics system for the reception of guidance intelligence and the production and conversion of error signals to control signals comprising, in combination: a supporting structure including a demonstration panel; a missile-positioning mechanism supported by said panel demonstrating the manner in which the characteristics of the received guidance intelligence and its equivalent derived signals vary in accordance with the position of the missile relative to the radar beam; a pitch-roll-yaw mechanism supported by said panel demonstrating the proDuction of error signals in response to deviations of the missile from a predetermined reference altitude relative to the radar beam axis; a control-wings mechanism supported by said panel demonstrating the manner in which the control signals effect changes in the attitudes of the control wings relative to the body of the missile; and a block diagram of the guidance and control system of the missile, depicted on said panel and illustrating the components and stages utilized to accomplish the reception of guidance intelligence and the production and conversion of error signals to control signals, the interrelationship of said mechanisms and their output signals with the components and stages in said block diagram being shown by means of connecting lines.
 7. A device as set forth in claim 6, wherein said missile-positioning mechanism includes: means simulating a nutating radar beam; means movable within the area covered by said nutating radar beam simulating the guided missile; and means responsive to the motion of said movable means indicating the changes which occur in the characteristics of the received guidance intelligence and the equivalent derived signals when the means simulating the guided missile is moved within the radar beam area.
 8. A device as set forth in claim 6, wherein said pitch-roll-yaw mechanism includes: means simulating the stabilizer-wing section of the guided missile, said means being manipulable in the yaw, pitch and roll planes to produce signals corresponding to the yaw, pitch and roll rate error signals produced in the guided missile; means, operable in response to movements of said stabilizer-wing simulating means in the yaw and pitch planes, simulating the yaw and pitch error-signal generators of the guided missile; means simulating the rate gyros of the guided missile and having associated means generating signals corresponding to the yaw, pitch and roll error signals produced in the guided missile; and means indicating the signals produced by said stabilizer-wing simulating means and said rate-gyro simulating means.
 9. A device as set forth in claim 6, wherein said control-wings mechanism includes: means simulating the control-wings section of the guided missile, the control wings thereon being movable; manipulable means simulating the control-wings positioning mechanism in the guided missile, manipulation of said last-named means operating to move the wings on said control wings simulating means; and manipulable means simulating the mechanisms in the missile which control the application of activating energy to said wing-positioning mechanism in response to said control signals.
 10. A device as set forth in claim 6, wherein said missile-positioning mehanism includes: a first circular disc representing the entire transverse cross-sectional area covered by a nutating radar beam; a second smaller circular disc representing the transverse cross-sectional area of the radar beam itself, said second disc affixed to said first disc so that the circumference of the former is circumscribed by and tangent to the circumference of the latter, both discs being translucent and mounted to the rear of said panel but visible from the front; motor means mounted on the rear of said panel operating to rotate said discs; a third disc having the cross-sectional shape of the guided missile; carriage means comprising a horizontal track movable vertically across the area covered by said first disc and a conveyer movable horizontally said track across the area covered by said first disc, said conveyer bearing with it said missile-shaped disc and light means projecting the image of said missile-shaped disc upon said first and second discs; a wire-and-pulley system operatively associated with said carriage means; control means coupled and applying power to said wire-and-pulley system, whereby said carriage means and said missile-shaped disc are caused to move correspondingly; a plurality of graphic representations of the guidance pulses constituting the receivEd guidance intelligence and a plurality of graphic representations of their derived equivalent signals, said representations located behind cut-outs in said support panel, the lower edges of said cut-outs serving as a zero reference level for said pulses and signals; a plurality of shafts bearing coaxial drums to which said representations are affixed for viewing through said cut-outs; a wire-and-pulley system, operatively associated with said wire-and-pulley system moving said missile-shaped disc, moving said shafts in accordance with the movements of said missile-shaped disc; and a pair of dial representations, each associated with a pair of indicator lamps, said dial representations showing guidance-pulse error signal amplitude by means of pointer effectively operated by said wire-and-pulley system moving said missile-shaped disc, one dial associated with the up-down positioning system and one dial with the left-right positioning system, and each indicator lamp in a pair indicating a different phase of the guidance-pulse error signals, said signals being connected to the correct indicator lamp by switch means effectively operated by said wire-and-pulley system moving said missile-shaped disc.
 11. A device as set forth in claim 6, wherein said pitch-roll-yaw mechanism includes; a fabricated imitation of a transverse section of said missile containing the stabilizer wings; a gimbal system mounting said imitation for yaw, pitch and roll movements; means operatively associated with said gimbal system producing signals in response to the yaw, pitch and roll movements of said imitation; means operatively associated with said gimbal system producing torsions in response to the yaw, pitch and roll movements of said imitation; a plurality of potentiometer representations having movable simulations of contact arms, said arms being operatively connected to said torsion-producing means; fabricated models of the rate gyros of the missile, each with its spinning axis in a different position so that each resists a different one of the three possible movements of the missile, yaw, pitch or roll; a plurality of levers projecting from said panel, each adjacent to and associated with a respective rate-gyro model, and a plurality of potentiometer means, each having a contact arm connected to be moved by a respective lever for the production of signals corresponding to the yaw, pitch and roll error signals produced in the missile; a plurality of electrical meters indicating the signals produced by said means associated with said gimbal system and said potentiometer means; and a flat, bullet-shaped member having a central aperture connected with its outer edge and a movable piston retained in said aperture representing the missile''s pressure-responsive error-signal generator.
 12. A device as set forth in claim 6, wherein said control-wings mechanism includes: a plurality of fabricated flat members mounted on the front of said panel, and representing the missile wing-actuating mechanisms, each member rectangularly shaped like the cross section of a piston chamber and retaining a manually movable piston within its central aperture; a plurality of fabricated flat members mounted on the front of said panel and representing the missile''s mechanisms for controlling the application of activating energy to its wing-actuating mechanisms, each member rectangularly shaped like the cross-section of a piston chamber and retaining a manually movable plunger within its central aperture; means indicating how movement of said plungers controls the communication of activating energy to said pistons; means indicating that said plungers are operable in response to said control signals; a fabricated imitation of the transverse section of the missile containing the control wings, the wings on said imitation being movable as in said missile; and wire-and-pulley systems connecting each of said pistons in said wing-positioning-mechanism representations to its respective wing so that manual movement of a pisTon correspondingly positions its associated wing. 